EP0818658A1 - Ringbrennkammer mit reduzierter Nox-Produktion - Google Patents

Ringbrennkammer mit reduzierter Nox-Produktion Download PDF

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Publication number
EP0818658A1
EP0818658A1 EP97401658A EP97401658A EP0818658A1 EP 0818658 A1 EP0818658 A1 EP 0818658A1 EP 97401658 A EP97401658 A EP 97401658A EP 97401658 A EP97401658 A EP 97401658A EP 0818658 A1 EP0818658 A1 EP 0818658A1
Authority
EP
European Patent Office
Prior art keywords
annular
internal
external
orifices
injection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP97401658A
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English (en)
French (fr)
Other versions
EP0818658B1 (de
Inventor
Jean-Paul Daniel Alary
Stéphane Jean-Marie Courtet
Michel André Albert Desaulty
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0818658A1 publication Critical patent/EP0818658A1/de
Application granted granted Critical
Publication of EP0818658B1 publication Critical patent/EP0818658B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a combustion chamber annular comprising an axis of symmetry, internal and external walls annular with respect to said axis, a bottom which extends transversely by report to said axis and which, in cooperation with said internal walls and external, delimits a combustion chamber which has an outlet downstream ring for the exhaust of combustion gases, a plurality fuel injectors arranged in openings in the bottom and a source of pressurized fuel.
  • the annular combustion chambers of the aeronautical turbomachines conventionally comprise, at the level of chamber bottom, fuel and air injection devices.
  • injection devices are, for example, under the form of bowls arranged at a certain distance from each other.
  • Each bowl has a fuel injection device, a swirl spin for fuel spray air and a row of holes for injecting air into the sprayed fuel cone.
  • the bowls being circular, it follows a significant number injection devices.
  • dead zones remain between each bowl, and the circumferential temperature profile is heterogeneous, this being linked at the injection points, the dead zones being, for their part, creating Nox.
  • US-A-2,920,449 discloses an annular chamber in which the chamber bottom has an annular opening delimited by two walls spaced cylindrical and through which air enters axially into the bedroom.
  • An annular injection manifold, with two rows of orifices radial, is arranged in this annular opening, and a diverging ring is provided downstream of the injection manifold to separate the combustion gases delivered in the combustion zone of the combustion chamber, in two annular flows directed respectively to the internal and external walls.
  • the aim of the present invention is to achieve homogeneity near-perfect fuel, in order to reduce Nox emissions and improve the temperature profile while reducing the number of parts.
  • the axes of the fuel injection ports are offset radially at an angle between 40 ° and 50 °.
  • each injector has two surfaces conical converging towards the interior of the combustion chamber on each of which open the orifices of a row of orifices fuel injection, said surfaces being connected upstream by a toric surface.
  • the toroidal part of an injection rail is embedded in a arched notch of a sheath which has two oblique walls at the entrance of said notch to allow positioning of said ramp in said notch during assembly, said sleeve being mounted with play in upstream of the internal and external tendrils between two successive spacers.
  • the internal and external ferrules have downstream of the ramp injection a plurality of oxidant injection ports.
  • the drawings show an annular combustion chamber 1, of axis of symmetry 2, which has an internal annular wall 4 and a wall outer annular 5 spaced radially from the inner wall 4. These two walls 4 and 5 are connected upstream by a chamber bottom 6, in order to delimit a combustion chamber 7 having an outlet downstream annular 8 by which the burnt gases are evacuated to a non-turbine represented.
  • the combustion chamber 1 is housed in a casing 9 delimited by an internal annular partition 10 and an external annular partition 11, radially spaced. This casing 9 is supplied upstream with compressed air by a diffuser 12 disposed downstream of a compressor, not shown, driven by the turbine.
  • the chamber bottom 6 disposed substantially transversely by relation to the axis of symmetry 2 is produced by two annular plates 14, 15 fixed respectively to the upstream ends of the inner 4 and outer 5 walls and extending towards each other, and two annular rings 16, 17 which delimit between them, upstream of the combustion zone 7a of the enclosure of combustion 7 an annular chamber 18 flared downstream.
  • the internal annular shell 16 is fixed at its downstream end to the outer edge of the annular plate 14, and it is extended radially inward by a heat shield 19 parallel to the annular plate 14.
  • the latter has air inlet orifices 20 of cooling, this air flowing through the annular slot 21 provided between the heat shield 19 and the inner wall 4.
  • a radial inner spin 22 is provided at the upstream end of the internal shroud 16.
  • the external annular shell 17 is fixed at its downstream end to the inner edge of the annular plate 15, and it is extended radially outwards by a heat shield 23 parallel to the annular plate 15.
  • the latter also has orifices 24 through which penetrates cooling air flowing through the slot 25 which separates the shield 23 and the outer wall 5.
  • a radial outer spin 26 is provided at the end upstream of the outer shell 17.
  • the internal 16 and external 17 tendrils are arranged radially at distance from each other, and they are connected upstream by a plurality radial spacers 30 regularly distributed around the axis of symmetry 2 which define arcuate openings therebetween 31.
  • a sheath 32 Upstream of each arched opening 31 and between two spacers successive 30, is disposed a sheath 32 which has a notch arched 33 which opens into opening 31.
  • This sheath 32 has at the entrance of the notch 33 two walls guide 34, 35 oblique, and it is mounted on the chamber bottom 6 with a radial and axial clearance allowing for thermal differences due to differences exhibits.
  • the fuel injection system has as many injectors fuel 40 that there are openings 31 in the chamber bottom 6.
  • Each injector 40 includes a radial injector body 41 and an injection rail 42 which fits into a notch 33 of a sleeve 32.
  • the injection manifold 42 has two conical surfaces 43, 44 which converge towards the interior of the combustion chamber 7 and which are connected upstream by a toric surface 45 whose diameter corresponds to the width notch 33.
  • Two rows of fuel injection ports 46, 47 lead respectively to the conical surfaces 43 and 44. The axes of these orifices 46 and 47 are inclined radially by about 45 °.
  • all of the injection ramps 42 thus forms a discontinuous annular ramp which divides the annular chamber 18 into an internal annular space 50 delimited by the internal ferrule 16 and the conical surface 43 and an annular space outer 51 delimited by the outer ring 17 and the conical surface 44 of the injection rails 42.
  • the internal annular space 50 is supplied with fuel by the row of orifices 46 and in spraying air by the internal spin 22.
  • the external annular space 51 is supplied with fuel by the row of orifices 47 and in atomizing air by the external spin 26.
  • the internal 22 and external 26 tendrils are provided in such a way that the air flows injected into the internal annular spaces 50 and external 51 are counter-rotating around the axis of symmetry 2, the air entering the space internal annular 50 swirling clockwise, view of the interior of the enclosure 7, and the air entering the annular space external 51 swirling anti-clockwise.
  • the fuel injection orifices 46 and 47 are inclined in such a way way that they inject the fuel respectively into the spaces annulars 50 and 51, in the case of circumferential circulation of the air flows feeding these spaces 50 and 51.
  • the conical parts of the inner 16 and outer 17 ferrules further comprising orifices 52, 53 for injecting air into the cones fuel from the annular spaces 50 and 51.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP97401658A 1996-07-11 1997-07-10 Ringbrennkammer mit reduzierter Nox-Produktion Expired - Lifetime EP0818658B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9608656 1996-07-11
FR9608656A FR2751054B1 (fr) 1996-07-11 1996-07-11 Chambre de combustion anti-nox a injection de carburant de type annulaire

Publications (2)

Publication Number Publication Date
EP0818658A1 true EP0818658A1 (de) 1998-01-14
EP0818658B1 EP0818658B1 (de) 2003-06-04

Family

ID=9493936

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97401658A Expired - Lifetime EP0818658B1 (de) 1996-07-11 1997-07-10 Ringbrennkammer mit reduzierter Nox-Produktion

Country Status (5)

Country Link
US (1) US5937653A (de)
EP (1) EP0818658B1 (de)
CA (1) CA2206184C (de)
DE (1) DE69722517T2 (de)
FR (1) FR2751054B1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102213427A (zh) * 2010-04-06 2011-10-12 通用电气公司 环形圈-歧管四级燃料分配器
EP2375163A3 (de) * 2010-04-06 2017-11-22 General Electric Company Segmentierter kranzförmiger Ringverteiler für einen quarternären Brennstoffverteiler
CN108139077A (zh) * 2015-10-06 2018-06-08 赛峰直升机发动机公司 用于涡轮发动机的环形燃烧腔室
CN111396927A (zh) * 2020-03-27 2020-07-10 中国科学院工程热物理研究所 二维阵列无传统旋流器的低污染燃烧装置

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US6279323B1 (en) * 1999-11-01 2001-08-28 General Electric Company Low emissions combustor
US7249461B2 (en) * 2003-08-22 2007-07-31 Siemens Power Generation, Inc. Turbine fuel ring assembly
FR2909163B1 (fr) * 2006-11-28 2011-02-25 Snecma Carenage de chambre de combustion de turbomachine.
DE102007043626A1 (de) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
DE102007061995B4 (de) * 2007-12-21 2012-03-01 Airbus Operations Gmbh Vorrichtung zum mechanisch entkoppelten Befestigen einer von Heißgas durchströmten Flugzeugkomponente
US8516820B2 (en) * 2008-07-28 2013-08-27 Siemens Energy, Inc. Integral flow sleeve and fuel injector assembly
US8549859B2 (en) * 2008-07-28 2013-10-08 Siemens Energy, Inc. Combustor apparatus in a gas turbine engine
US8528340B2 (en) * 2008-07-28 2013-09-10 Siemens Energy, Inc. Turbine engine flow sleeve
ATE528589T1 (de) * 2008-08-04 2011-10-15 Siemens Ag Swirler
US20100071377A1 (en) * 2008-09-19 2010-03-25 Fox Timothy A Combustor Apparatus for Use in a Gas Turbine Engine
US9541292B2 (en) 2013-03-12 2017-01-10 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9127843B2 (en) 2013-03-12 2015-09-08 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9958161B2 (en) 2013-03-12 2018-05-01 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
FR3011317B1 (fr) * 2013-10-01 2018-02-23 Safran Aircraft Engines Chambre de combustion pour turbomachine a admission d'air homogene au travers de systemes d'injection
US10578021B2 (en) * 2015-06-26 2020-03-03 Delavan Inc Combustion systems
RU2015156419A (ru) 2015-12-28 2017-07-04 Дженерал Электрик Компани Узел топливной форсунки, выполненный со стабилизатором пламени предварительно перемешанной смеси
US10295190B2 (en) 2016-11-04 2019-05-21 General Electric Company Centerbody injector mini mixer fuel nozzle assembly
US10393382B2 (en) 2016-11-04 2019-08-27 General Electric Company Multi-point injection mini mixing fuel nozzle assembly
US10465909B2 (en) 2016-11-04 2019-11-05 General Electric Company Mini mixing fuel nozzle assembly with mixing sleeve
US10352569B2 (en) 2016-11-04 2019-07-16 General Electric Company Multi-point centerbody injector mini mixing fuel nozzle assembly
US10724740B2 (en) 2016-11-04 2020-07-28 General Electric Company Fuel nozzle assembly with impingement purge
US10634353B2 (en) 2017-01-12 2020-04-28 General Electric Company Fuel nozzle assembly with micro channel cooling
US20180335214A1 (en) * 2017-05-18 2018-11-22 United Technologies Corporation Fuel air mixer assembly for a gas turbine engine combustor
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly

Citations (8)

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US2552851A (en) * 1949-10-25 1951-05-15 Westinghouse Electric Corp Combustion chamber with retrorse baffles for preheating the fuelair mixture
US2920449A (en) * 1954-07-20 1960-01-12 Rolls Royce Fuel injection means for feeding fuel to an annular combustion chamber of a gas turbine engine with means for dividing the air flow
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
GB2057672A (en) * 1979-07-04 1981-04-01 Rolls Royce Gas turbine combustion chamber
EP0059490A1 (de) * 1981-03-04 1982-09-08 BBC Aktiengesellschaft Brown, Boveri & Cie. Ringbrennkammer mit Ringbrenner für Gasturbinen
GB2098719A (en) * 1981-05-20 1982-11-24 Rolls Royce Gas turbine engine combustion apparatus
GB2211596A (en) * 1985-08-23 1989-07-05 Gen Electric Gas turbine engine carburetor
GB2252152A (en) * 1991-01-22 1992-07-29 Gen Electric Combustor dome of a gas turbine engine

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US3736746A (en) * 1971-08-13 1973-06-05 Gen Electric Recirculating annular slot fuel/air carbureting system for gas turbine combustors
US4158959A (en) * 1978-03-02 1979-06-26 Camco, Incorporated Apparatus for measuring the physical properties of material
FR2698157B1 (fr) * 1992-11-18 1994-12-16 Snecma Système d'injection aérodynamique de chambre de combustion.
US5331805A (en) * 1993-04-22 1994-07-26 Alliedsignal Inc. Reduced diameter annular combustor
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2552851A (en) * 1949-10-25 1951-05-15 Westinghouse Electric Corp Combustion chamber with retrorse baffles for preheating the fuelair mixture
US2920449A (en) * 1954-07-20 1960-01-12 Rolls Royce Fuel injection means for feeding fuel to an annular combustion chamber of a gas turbine engine with means for dividing the air flow
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
GB2057672A (en) * 1979-07-04 1981-04-01 Rolls Royce Gas turbine combustion chamber
EP0059490A1 (de) * 1981-03-04 1982-09-08 BBC Aktiengesellschaft Brown, Boveri & Cie. Ringbrennkammer mit Ringbrenner für Gasturbinen
GB2098719A (en) * 1981-05-20 1982-11-24 Rolls Royce Gas turbine engine combustion apparatus
GB2211596A (en) * 1985-08-23 1989-07-05 Gen Electric Gas turbine engine carburetor
GB2252152A (en) * 1991-01-22 1992-07-29 Gen Electric Combustor dome of a gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102213427A (zh) * 2010-04-06 2011-10-12 通用电气公司 环形圈-歧管四级燃料分配器
CN102213427B (zh) * 2010-04-06 2015-05-20 通用电气公司 环形圈-歧管四级燃料分配器
EP2375163A3 (de) * 2010-04-06 2017-11-22 General Electric Company Segmentierter kranzförmiger Ringverteiler für einen quarternären Brennstoffverteiler
CN108139077A (zh) * 2015-10-06 2018-06-08 赛峰直升机发动机公司 用于涡轮发动机的环形燃烧腔室
CN108139077B (zh) * 2015-10-06 2020-09-15 赛峰直升机发动机公司 用于涡轮发动机的环形燃烧腔室
US10895383B2 (en) 2015-10-06 2021-01-19 Safran Helicopter Engines Ring-shaped combustion chamber for a turbine engine
CN111396927A (zh) * 2020-03-27 2020-07-10 中国科学院工程热物理研究所 二维阵列无传统旋流器的低污染燃烧装置

Also Published As

Publication number Publication date
DE69722517T2 (de) 2004-04-22
EP0818658B1 (de) 2003-06-04
US5937653A (en) 1999-08-17
FR2751054A1 (fr) 1998-01-16
FR2751054B1 (fr) 1998-09-18
CA2206184A1 (fr) 1998-01-11
DE69722517D1 (de) 2003-07-10
CA2206184C (fr) 2000-10-31

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